CN102422014A - Combined wing and turbine device for improved utilization of fluid flow energy - Google Patents

Combined wing and turbine device for improved utilization of fluid flow energy Download PDF

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Publication number
CN102422014A
CN102422014A CN2010800186937A CN201080018693A CN102422014A CN 102422014 A CN102422014 A CN 102422014A CN 2010800186937 A CN2010800186937 A CN 2010800186937A CN 201080018693 A CN201080018693 A CN 201080018693A CN 102422014 A CN102422014 A CN 102422014A
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CN
China
Prior art keywords
wing
edge
rotor
location
equipment
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Granted
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CN2010800186937A
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Chinese (zh)
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CN102422014B (en
Inventor
瑟伦·邦-默勒
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Individual
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Individual
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Priority claimed from DKPA200900546A external-priority patent/DK176999B1/en
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Publication of CN102422014A publication Critical patent/CN102422014A/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03D—WIND MOTORS
    • F03D13/00—Assembly, mounting or commissioning of wind motors; Arrangements specially adapted for transporting wind motor components
    • F03D13/20—Arrangements for mounting or supporting wind motors; Masts or towers for wind motors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03D—WIND MOTORS
    • F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor 
    • F03D1/02—Wind motors with rotation axis substantially parallel to the air flow entering the rotor  having a plurality of rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03D—WIND MOTORS
    • F03D3/00—Wind motors with rotation axis substantially perpendicular to the air flow entering the rotor 
    • F03D3/002—Wind motors with rotation axis substantially perpendicular to the air flow entering the rotor  the axis being horizontal
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03D—WIND MOTORS
    • F03D3/00—Wind motors with rotation axis substantially perpendicular to the air flow entering the rotor 
    • F03D3/02—Wind motors with rotation axis substantially perpendicular to the air flow entering the rotor  having a plurality of rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03D—WIND MOTORS
    • F03D3/00—Wind motors with rotation axis substantially perpendicular to the air flow entering the rotor 
    • F03D3/06—Rotors
    • F03D3/062—Rotors characterised by their construction elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03D—WIND MOTORS
    • F03D9/00—Adaptations of wind motors for special use; Combinations of wind motors with apparatus driven thereby; Wind motors specially adapted for installation in particular locations
    • F03D9/30—Wind motors specially adapted for installation in particular locations
    • F03D9/34—Wind motors specially adapted for installation in particular locations on stationary objects or on stationary man-made structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03D—WIND MOTORS
    • F03D9/00—Adaptations of wind motors for special use; Combinations of wind motors with apparatus driven thereby; Wind motors specially adapted for installation in particular locations
    • F03D9/20—Wind motors characterised by the driven apparatus
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/90—Mounting on supporting structures or systems
    • F05B2240/91—Mounting on supporting structures or systems on a stationary structure
    • F05B2240/911—Mounting on supporting structures or systems on a stationary structure already existing for a prior purpose
    • F05B2240/9112—Mounting on supporting structures or systems on a stationary structure already existing for a prior purpose which is a building
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02B—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO BUILDINGS, e.g. HOUSING, HOUSE APPLIANCES OR RELATED END-USER APPLICATIONS
    • Y02B10/00—Integration of renewable energy sources in buildings
    • Y02B10/30—Wind power
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/70—Wind energy
    • Y02E10/72—Wind turbines with rotation axis in wind direction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/70—Wind energy
    • Y02E10/728—Onshore wind turbines
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/70—Wind energy
    • Y02E10/74—Wind turbines with rotation axis perpendicular to the wind direction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P70/00—Climate change mitigation technologies in the production process for final industrial or consumer products
    • Y02P70/50—Manufacturing or production processes characterised by the final manufactured product

Abstract

There is provided a device for production of electrical, mechanical or hydraulic energy by using wind or other fluid currents. This is achieved by blocking a portion of the flow through an edge positioned wing (1) alone or in combination with a longitudinal wing (2). The invention includes an edge positioned wing (1), a rotor (5), a bottom profile (4), gable profiles / lamellas (3) and turbine lamellas (12) to focus the flow towards the rotor (5). Perforations (10) or gaps (7) in or between the wings may improve the flow through or around the turbine.

Description

The combination wing and the turbine equipment that are used for the improvement utilization of fluid flow energy
Technical field
The present invention relates to a kind of being used for through using wind or fluid flow energy to produce the equipment of electric energy, mechanical energy or hydraulic pressure ability, said equipment comprises: at least one rotor, wherein said wind or fluid stream make rotor around its axis rotation; At least one base portion profile elements; And at least one wing.
Background technique
Prior art systems is all sought to come fluid flow to concentrate to the funneling effect of the fluid stream that becomes a mandarin.
Disclosed the equipment that increases wind energy through the wind turbine that is positioned at the roof on January 3rd, 2008 with the disclosed patent application of publication number WO 2008/001080 A1 (Taylor); Said roof forms the lower limits of each rotor; And be equipped with the wing of horizontal arrangement; The said wing has with respect to the directed string in the tangent ground of said rotor, the upper bound of the said turbo machine of said wing one-tenth.This document has only disclosed that the wing or the wing sections of tangent ground deflection---it has with respect to said wing chord indent, asymmetric characteristic.This layout forms funnel through the place ahead at turbo machine and has utilized the direct influence of wind on turbine inlet.This produces limited " swabbing effect " at leeward side.
The present invention seeks obtaining bigger concentrating aspect the deceleration through the wing of location, one or more edge, thus, because the dynamic pressure drop of the increase that is caused by the retardance zone of the wing of location, edge obtains the channel effect that increases.
Summary of the invention
The present invention provides a kind of and is used for through using wind or other fluid stream to generate the equipment of electric energy, mechanical energy or hydraulic pressure ability, and said equipment is characterised in that:
Be connected to generator said rotor axial, and
The said wing is the location, edge, makes its string towards said rotor orientation.
The maximum dynamic pressure reduction that this allows between turbo machine front and rear increases " swabbing effect (the suction effect) " of leeward side thus.
According to claim 2, the wing of location, said edge manufactures to have solid or hollow-core construction.
According to claim 3, the wing of location, said edge manufactures at least a portion of the said wing has perforation.According to claim 4, the wing of location, said edge manufactures and is equipped with the edge notch.This guarantees that said equipment can be adapted to view, and perhaps given architectural design or building perhaps just provide different designs.In addition, said equipment is at said wind or the fluid out-of-date better flow performance that provides of flowing through.
According to claim 5, the wing of location, said edge has prismatic, smooth, protrusion, recessed or the different dynamic (dynamical) designs of streamline.
Referring to claim 6, in certain embodiments, the wing chord of location, edge is with an angular orientation, and this angle is in perpendicular to the angle of rotor spin axis and is tangential between the angle of rotor periphery.The wing of location, edge can be installed at least one hanger according to claim 7, and said hanger comprises that the wing of location, said edge can be around the spin axis of its rotation.
In a preferred embodiment, referring to claim 8, at least one vertical wing is between the wing and rotor of location, edge, and its string is substantially perpendicular to rotor.According to claim 9, vertically the wing can be integrated in the wing of location, edge.According to claim 10, vertically the wing can be a periphery that is smooth, protrusion or recessed or that be adapted to rotor.Perforation during this wing that will be similar to the location, edge designs provides better flow characteristic when wind or fluid stream process turbine flow passage.
According to claim 11, rotor design is vertical, level, propeller type or screw type turbo machine.
According to claim 12, in a special preferred embodiment, at least one thin slice is arranged in the turbine flow passage (8) that is defined by the wing of location, edge and bottom profile part.This guarantees that wind or fluid stream are directed towards the turbo machine guiding rather than along turbo machine.
According to claim 13, the bottom profile part is a geometrical shape that is smooth, crooked or that be adapted to rotor.
According to claim 14, at least one turbo machine thin slice is positioned at the turbine flow passage.This will guarantee that also wind or fluid stream is guided towards turbo machine.
In certain embodiments (for example claim 15), the wing of location, two or more edge is oriented to their string facing to rotor.
Description of drawings
Hereinafter, will be with reference to explained the present invention, in said accompanying drawing:
Figure 1A illustrates the said system among the embodiment with simple, smooth, that locate at edge wing,
Figure 1B is illustrated in system described in the Figure 1A that has perforation in the wing,
Fig. 1 C is illustrated in system shown in the Figure 1A that has random otch in the edge of the wing,
Fig. 1 D is illustrated in system shown in the Figure 1A that has the harmony otch in the edge of the wing,
The edge that Fig. 1 E is illustrated in the wing has system shown in Figure 1A of perforation and otch,
Fig. 1 F illustrates the said system among the embodiment of the wing of the edge location with bulk,
Fig. 2 A illustrates the said system among second embodiment with smooth vertical wing,
Fig. 2 B illustrates the cross section of system shown in Fig. 2 A,
Fig. 2 C illustrates the system among second embodiment of the vertical wing with bulk,
Fig. 2 D illustrates the cross section of system shown in Fig. 2 C,
Fig. 3 A-B illustrates the 3rd embodiment's with turbine inlet thin slice system,
Fig. 4 A illustrates the cross section of the turbo machine that adapts to any fluid stream,
Fig. 4 B illustrates the cross section of the turbo machine that adapts to one-sided fluid stream,
Fig. 5 A illustrates the system among the 4th embodiment with the propeller type rotor that is held,
Fig. 5 B illustrates the system among the 4th embodiment of the propeller type rotor with rotation,
Fig. 5 C illustrates the system among the 5th embodiment with upright rotor,
Fig. 6 A-C illustrates the system that is cascade construction,
Fig. 7 A-D illustrates said system and is installed in the embodiment on ridge and the angle, room,
Fig. 8 A-C illustrates the embodiment of the cascade construction on several angles that are installed in ridge and house,
Fig. 9 A-C illustrates the system in the deflection example,
Figure 10 A-C illustrates the system in another deflection example,
Figure 11 A-D illustrates the system among the 6th embodiment with the wing of locating at a plurality of edges,
Figure 12 illustrates the system in the deflection example with the suspension point that closes on the bottom profile part,
Figure 13 A-B illustrates the system that has in the deflection example of the suspension point of the string of edge location wing,
Figure 14 A-J illustrates the different shape of edge location wing,
Figure 15 A-C illustrates the system among the 7th embodiment, wherein said system building in the roof,
Figure 16 A-B illustrate be built in the roof with system like the system class shown in Figure 1B, and
Figure 17 illustrates the cascade construction of the system that is installed in the owned building corners.
Embodiment
Through using at the compelled cut-through thing of fluid or can producing pressure reduction when passing narrow passage and in fluid stream, produce the static structure of velocity variations, the present invention uses wind and fluid flow energy with a kind of new mode.
The present invention relates to be used for utilize the system of the fluid flow energy of wind or other streaming flow.The present invention uses new method to utilize fluid flow energy, it is characterized in that, one or more static wing stops the part of said fluid stream, and another part perhaps directly passes through above turbo machine through turbo machine simultaneously.Said wing system is characterised in that; Allow maximum air flow through turbo machine; Allow a part of air-flow between the turbo machine and the vertical wing, to pass in addition, perhaps pass slit or pass perforation, perhaps allow the lower limb of the said wing or the coboundary that the lower limb profile elements forms turbo machine.
The wing (1) of location, edge can be smooth fully, or possesses aerodynamic design, and their wing chord is towards the spin axis of turbo machine.In addition, the wing (1) of location, edge has symmetrical structure substantially with respect to its string.The bottom profile part (4) that is oppositely arranged with the edge of the said wing (1) limits the lower boundary of turbine flow passage (8), and rotor (5) is positioned at said turbine flow passage.
The wing (1) of edge location can with one or more wing/profile elements (2) combination, the said wing/profile elements (2) is located such that their bottom represents the coboundary of turbine chamber (8).The lower limb of the wing (1) of the top of the said wing/profile elements (2) and edge location forms as one, and forms one or more slit (7) or perforation (10) in the over top (closely) of the said wing/profile elements (2) or the top of closing on the said wing/profile elements (2).If, omit the said wing/profile elements (2), perforation (10) can be positioned on the wing (2) of location, edge.
Said system can also have one or more thin slice (3); Said thin slice (3) is used for said vertical wind field of deflection or fluid field of flow; To force said fluid stream through turbo machine chamber (8), slit (7) or perforation (10); And through the wing (1) of location, said edge, rather than the wing (1) that is parallel to location, said edge passes.Said thin slice (3) has also been strengthened said structure, and can be designed as straight, recessed, protrusion or its any combination.
Said system is based on the system of ridge, and has utilized the following ability of wind with other fluid streams, must around static structures, can produce pressure and velocity variations through out-of-date when said fluid flows that is:.Opposite with known similar system; The present invention uses, and simple, the static obstruction wing produces low pressure; The said fluid stream of said low-pressure suction makes it through turbo machine, and said low pressure is caused by the dynamic differential pressure of the increase between inlet side and the leeward side, and " swabbing effect " of leeward side increases thus.
The effect that obtains is the higher pressure reduction of turbo machine both sides.Perforation (10) in the slit between the said wing and the turbo machine (7) and/or the wing is used for producing the turbo machine (5) and be that quick and the stable fluid of directly walking around said turbo machine (5) flows of flowing through.
The system is characterized in that and to combine with any known rotor type, and can produce the effect of these rotors with mode simple and attractive in appearance.This system is particularly suitable for being positioned statically spine, skyscraper, view protuberance etc. and locates.
The present invention comprises the wing (1), rotor (5) and the thin slice (3) of location, said edge at least, and it is attached to wall, roof, angle, room, view protuberance and spine, river bed, waterfall or similarly mobile intensive position under water.
Said system can be designed to make its bidirectional-movement, and by from the fluid stream of both sides and work.
Said system design perhaps is designed to be positioned on these structures for making it can be built in building, view, the earth or similar position.
In the explanation below, " level " rotor type is defined as has the rotor wing and running shaft and the fluid stream rotor along the running shaft longitudinal movement." vertically " rotor type is defined as has the rotor wing and running shaft and fluid stream moves to the rotor on the said running shaft along its length with the right angle." string " is defined as the straight line between said wing front edge and the rear edge (the upper and lower edge of the wing of location, said edge).
The system zero parts
With reference to the top explanation and the description of drawings and the embodiment of back, the reference character of component of the present invention is placed in the bracket, and after the component title.
(1) wing of location, edge:
I. be oriented said string facing to (against) said rotor
Ii. for so-called vertical turbo machine (Sa Woniusi (Savonius) formula, that reach Lille (Darrieus) (Banki) formula, double click type, Ou Si Burger (Ossberger) formula or similar); The string of the wing of edge location point to running shaft or can bending at an angle, make that the outer radius of said string and said rotor is tangent.
Iii. (be commonly referred to propeller cavitation for horizontal turbo machine; The sort of propeller cavitation on the Vestas wind turbine for example); The string of the wing of location, said edge is parallel to the plane vertical with spin axis, if perhaps at an angle with respect to this plane---and said turbo machine rotation.
The effect of the wing of location, iv. said edge is: the fluid stream through stopping the turbo machine of flowing through than large size, the maximum dynamic pressure reduction between the front and rear portions of turbine is provided.
V. in order to obtain flow characteristic preferably, the said wing can be perforated or notch is set in a different manner, makes the part of said stream can pass said perforation and notch.The wing (1) of location, said edge can have hollow or solid construction.
(2) vertical wing/turbine flow coboundary wing:
I. can be integrated into the wing (1) of location, said edge.
Ii. for vertical turbo machine, said string is vertically or almost perpendicular to spin axis.
Iii. can be periphery that is smooth, protrusion, recessed or that on aerodynamics, adapt to said rotor.
Iv. can equally with the wing (1) of location, said edge be formed with perforation, notch, and structurally can be hollow or solid.
(3) thin slice and gable shape profile elements:
I. through comprising at least two or the unlimited a plurality of thin slices of as many as/gable shape profile elements, said system is divided at least one or goes up extremely unlimited a plurality of turbine flow passages (8).
Ii. be used for the supporting of vertical turbine rotor axle or be used to pass the opening of rotor.
Iii. flow thin slice and supporting element as fluid, and carry the wing (1) of location, edge, vertical wing (2) and rotor (5).Can also only carry the wing (1) of location, edge, perhaps only carry vertical wing (2).
Iv. the thin slice in the gable can be designed as and has opening, and said opening is formed for the supporting of rotor shaft.Intermediate strap can be designed to have the opening that is used for continuous rotor (5), or be formed for an opening that runs through the supporting of rotor shaft or two rotor shafts that link.
V. as the attachment point on specific landform, roof, wall or the analog.
Vi. can equally with the wing (1) of location, said edge be formed with perforation, notch, and structurally can be hollow or solid.
(4) bottom profile part/turbine inlet lower boundary profile elements:
I. form the bottom of turbo machine.Said bottom need not be flatly directed, but can place vertically or place with any other direction according to local circumstance.
Ii. the bottom profile part can be made up of the fastening front surface---such as wall, roof, the earth or rock---of working as on it of said system.
Iii. be similar to vertical wing (2), the bottom profile part can be fully smooth, bending or be adapted to the turbo machine periphery.
(5) rotor:
I. can with any known turbines type combination.
Ii. in vertical rotor type (" cross-flow wind turbine "), rotor produces rotating energy in gear mechanism housing (6), and said rotating energy changes into electric energy, mechanical energy or hydraulic pressure ability in gear mechanism housing (6).
Iii. for the turbo machine (propeller cavitation) of horizontal type, energy response produces in the turbo machine of rotor shaft in centralized positioning.At this, rotating energy changes into electric energy, mechanical energy or hydraulic pressure ability.
(6) gear mechanism housing:
I. for vertical rotor type, said transmission is carried out at the gear mechanism housing that is positioned at system end portion gable shape part.
Ii. for long transmission system, housing can be built in the thin slice (3), and suitably adapts to the geometrical shape of thin slice.
Iii. in the time of in being inserted in the roof, gear mechanism housing can completely or partially be built in the roof, and generator, gear-box or similar energy input mechanism will be safeguarded from the inboard on roof thus.
(7) gap:
I. forming the gap between the wing (1) and the wing (2) and between the gable shape wing (9) and gear mechanism housing (6), ridge or other supports.This is similar to the slit on the conventional wing.
Ii. said gap can perhaps be divided into less a plurality of sections extending from thin slice (3) to the whole length of thin slice (3).Said gap in the gable shape wing (9) can be total length or be divided into less a plurality of sections.
(8) turbine flow passage:
I. said turbine flow passage by the wing (1) of edge location or vertically the wing (2), bottom profile part (4) and thin slice (3) layout and constitute.
Ii. said turbine flow channel interior can have thin slice (12) makes the fluid stream deflection that flows into and flow out.
(9) the gable shape wing:
I. the gable shape wing is for being configured with the side direction stiffening effect.
Ii. the gable shape wing increases barrier zones, so that big pressure reduction between the front and rear of turbine flow passage (8), occurs.
Iii. can be the same with the wing (1) of edge location, comprise some other wings stacked on top of each other and/or have perforation (10) and/or have the edge (11) of offering notch.
Iv. can form the wing (1) of following edge location and the profile of vertical wing (2), perhaps have attractive in appearance or ornamental profile, slit/gap and perforation.
(10) perforation in the wing:
I. be used for following purpose: produce turbulent flow (vortices) at leeward side, generation is more flowed near the fluid of laminar flow thus.Its with the conventional wing on the identical principle of slit work.
Ii. can be circle, square or random geometry, can comprise attractive in appearance or ornamental design.
(11) jagged wing edge:
I. the edge of the wing can be jagged or offer the notch that is similar to perforation (10), and its near surface at the wing (1) that leeward side (1) is located on the edge of produces little turbulent flow, with vortex generator identical effect is arranged.
Ii. can optionally design, comprise the characteristic that can have decoration or aesthetic property.
(12) turbine flow passage thin slice:
I. the inside of turbine flow passage (8) can have thin slice (2) and comes the fluid that flows into and flow out is flow to line deflection.
Illustrate in greater detail the present invention below in conjunction with example.
Figure 1A to 1F illustrates the simplest embodiment of the present invention; Said simple embodiment comprises the wing (1) of location, edge; The wing of location, said edge has towards the directed string of rotor (5), and the wing (1) and rotor (5) that gable shape profile elements (3) is located said edge remain on said rotor shaft place.The lower boundary of turbine flow passage (8) is limited bottom profile part (4), and said gable shape profile elements (3) is attached on the said bottom profile part (4).The coboundary of turbine flow passage (8) is limited on the wing (1) of location, edge.Rotor (5) can be designed as the vertical rotor that for example is used for double click type turbo machine, Ou Si Burger or cross-flow wind turbine (Banki, Ossberger or Cross Wind Turbine).
Figure 1A illustrates the present invention with wing (1) simple, smooth, the location, edge, and the said wing has towards the directed string of rotor (5).
Figure 1B illustrates the embodiment similar with Figure 1A, wherein, in the wing (1) of location, said edge, has perforation (10).
Fig. 1 C and Fig. 1 D illustrate the embodiment similar with Figure 1A, and wherein, the wing (1) of location, said edge is formed with notch (riffled).
Fig. 1 C is illustrated in the edge notch (11) of sawtooth form of edge of the wing (1) of edge location.
Fig. 1 D illustrates the edge notch (11) of the coordination of the cut forms in the wing (1) of locating at the edge.
The notch (11) of the form that the perforation (10) in the wing (1) that locate at the peculiar edge that Fig. 1 E shows the wing (1) that is incision edge location and edge is combined.This makes this system represent with mode simple and attractive in appearance.
The embodiment of the invention shown in Fig. 1 F has the wing (1) of the location, edge of bulk, and the wing (1) of location, said edge has the different surface profile geometries, and its string is oriented towards rotor (5).
Fig. 2 A to 2D illustrates specific embodiment of the present invention, has introduced smooth vertical wing (2) between the wing that this embodiment locatees on the edge of (1) and the rotor (5).This has produced gap (7), and gap (7) have and aforementioned perforation (10) identical functions.Vertically the lower limb of the wing (2) is at the top edge of this expression turbine flow passage (8).
Fig. 2 B illustrates embodiment's shown in Fig. 2 A cross section.
The embodiment of the invention shown in Fig. 2 C has vertical wing (2) of long bulk, and said vertical wing is with the mode of formation perforation (10) and the wing (1) combination of location, edge.
Fig. 2 D illustrates embodiment's shown in Fig. 2 C cross section.
Fig. 3 A illustrates the specific embodiment with turbine flow passage thin slice (12) of the present invention.
Fig. 3 B illustrates the specific embodiment with vertical wing (2) and turbine flow passage thin slice (12) of the present invention.
Fig. 4 A and 4B illustrate the sectional view that is adapted to the turbine flow passage (8) of rotor (5) geometrical shape through the geometry in particular of vertical wing (2) and bottom profile part (4).
Fig. 4 A illustrates the symplex structure of adaptation from the turbine flow passage (8) of any fluid stream of both sides.
Fig. 4 B illustrates the symplex structure of adaptation from the turbine flow passage (8) of the one-sided fluid stream of main direction.
Fig. 5 A illustrates specific embodiment of the present invention, and this embodiment has horizontal rotor (for example propeller type rotor), and this rotor is fixed with the parallel mode of the wing (1) of location, edge with rotor plane.
Fig. 5 B illustrates the specific embodiment with propeller type rotor of the present invention, and this rotor can pivot with the wing (1) that is positioned at edge location and the central point between the mobile thin slice (3).
Fig. 5 C illustrates one embodiment of the invention, and its rotor (5) is orientated as and made its spin axis along the wing (1) of location, edge and the cross-shaped portion of mobile thin slice (3).Rotor (5) can be designed to vertical turbo machine, for example has the Sa Woniusishi (Savonius) of the propeller shape wing or reaches Lille formula (Darrieus) turbo machine.
Fig. 6 A-6C illustrates the embodiment of the invention of cascade form (cascade style), and wherein the embodiment of the invention relates to Figure 1A-1F, 2A-2D, 3,4A-4B and 5A-5C and all forms, and it can be any quantity.
Fig. 7 A-7D illustrates a preferred form of the present invention, and wherein bottom profile part (4) is formed by local surfaces, have 0 the degree and 180 the degree between arbitrarily angled, it is depicted as and is installed on any roof and the angle, room.In example, the gable shape wing (9) and gear mechanism housing (6) are shown.Can omit the gable shape wing (9), but this will mean power loss.If the conversion of rotating energy realizes through the direct interaction between gable thin slice (3) and the rotor (5), can omit gear mechanism housing (6) so.
Fig. 8 A-8B illustrates the preferred embodiments of the present invention, wherein, introduces the wing (2) of long bulk on the edge of between the wing (1) of location and the rotor (5).
Fig. 8 B shows cascade unit of the present invention, and said cascade unit produces three turbine flow passages (8).Rotor (5) is embedded in the gable shape profile elements (3); And connect internally through shared rotor shaft; Said shared rotor shaft is passed to rotating energy in the gear mechanism housing (6), and said rotating energy changes into electric energy, mechanical energy or hydraulic pressure ability in said gear mechanism housing (6).At last, in order laterally to strengthen and for reason attractive in appearance, the present invention further is equipped with the gable shape wing (9).
Fig. 8 C illustrates the embodiment of Fig. 8 B---and it is installed on the building with a plurality of quantity, and is installed in all edges and ridge place.
Fig. 9 A and 9B illustrate an example of the present invention, and wherein angle beta is divided into the bottom profile part with center line C LTwo half equal ones of mark.The wing (1) of angle α marker edge location is from the deflection of bottom profile part (4) summit and center line cross-shaped portion arbitrarily.
Fig. 9 C illustrates Fig. 9 B embodiment who is installed on the bight (building that for example has flat roof).Fig. 9 C is depicted as with wall and roof as bottom profile part (4).
Figure 10 A and 10B illustrate crooked example of the present invention, and wherein angle beta is divided into the bottom profile part with center line C LTwo half equal ones of mark.The wing (1) of angle α marker edge location is from the deflection of the cross-shaped portion of rotor (5) wheel hub and center line arbitrarily.
Figure 10 C illustrates Figure 10 B embodiment who is positioned on the bight (building that for example has flat roof).Figure 10 C is depicted as with wall and roof as bottom profile part (4).
Figure 11 A-11D illustrates the example with a plurality of edges location wings (1).According to the crooked principle shown in Figure 10 A and the 10B, the present invention can have the wing of the location, edge of unlimited amount on principle.
Figure 11 A and 11B illustrate the example of enforcement, the wing (1) of location, two edges is wherein arranged, and string are oriented towards rotor (5).
Figure 11 A illustrates the embodiment of the invention of the wing (1) with location, two edges with sectional view.
Figure 11 B goes out to have the embodiment of the invention of two wings (1) with three-dimensional icon.
Figure 11 C and 11D illustrate the example of enforcement, the wing (1,1 ', 1 ") of location, three edges is wherein arranged, and string are oriented towards rotor (5).Substituting ground, the said wing (1 ', 1 ") is designed to be similar to the thin slice (12) of turbine inlet.
Figure 11 C illustrates the embodiment of the invention with three assistants (1) with sectional view.Angle a, q, s and y represent arbitrarily angled with respect to bottom profile part (4).
Figure 11 D goes out to have the embodiment of the wing of location, three edges with three-dimensional icon.
Example of the present invention shown in Figure 12 be about the wing (1) of edge location around the suspension point of the location, top of closing on bottom profile part (4), because fluid stream influences the mechanical deflection that produces; Wherein, the edge located of the wing (1) will be oriented to said string facing to rotor (5) under unaffected state.The deflection angle of string is represented with angle α.This deflection can be omitted or the embodiment that is arranged under vertical wing (2) occurs in thin slice (3).Thus, the wing (1), the gable shape wing (9) and possible vertical wing (2) of location, edge form individual unit.
Figure 13 A and 13B illustrate the related example of the present invention with aforementioned arbitrary embodiment, wherein the wing (1) of edge location can around along the suspension point of the string of the wing of location, edge, near the wing edge of rotor (5) to being positioned at rotor (5) arbitrfary point deflection afterwards along the string of the wing of location, edge.Said deflection can be fix or hover ground suspend, thereby can produce according to the effect of the stream of the fluid on the wing (1) of location, edge, wherein, this string has the tangent characteristic about rotor (5).
Figure 14 illustrates the example of several possibility shapes of the wing (1) of locating at the edge.Said string is illustrated by the broken lines.
Figure 14 A illustrates the smooth wing fully.
Figure 14 B illustrates the avette wing.
Figure 14 C illustrates the prismatic wing.
Figure 14 D illustrates the lacrimal wing.
Figure 14 E illustrates the circular edge wing and sharp edges wing amalgam between the two.
Figure 14 F illustrates the oblong wing that sphering is handled that carried out.
Figure 14 G illustrates avette, the lacrimal wing.
Figure 14 H illustrates has the wing wide, planar base portion, vertical wing (2) one of the wing (1) of said base portion and location, edge.
Figure 14 I illustrates has the wing wide, the sphering processing, protrusion base portion, vertical wing (2) one of the wing (1) of wherein said base portion and location, edge.
Figure 14 J illustrates the wing with wide recessed base portion, vertical wing (2) one of the wing (1) of wherein said base portion and location, edge.
Figure 14 A1 to 14J4 illustrates the further mode of execution of previous designs.The thick and heavy embodiment of symbol 1 expression.The embodiment of symbol 2 expression tape punchings.Symbol 3 expression edges have the embodiment of notch.Symbol 4 expressions form of implementation square, perforation.
Figure 15 A to 15C illustrates the embodiment of the invention that is embedded in fully in the roof, and wherein, only the wing (1) of location, edge is higher than ridge.Vertically the wing (2) illustrates in a preferred embodiment, and wherein vertical wing is designed to follow the shape of all the other roof structures.Said embodiment is designed to make that gear mechanism housing (6) manufactures the part on roof, can safeguard transmission device from the ceiling board below thus.Said turbine flow passage (8) asymmetricly transform be adapted to double click type/Ou Si Burger formula or similar vertical-type rotor.Vertically the geometrical shape of the upside of the wing (2) will be transformed being adapted to the ridge at said top, and is protruding again of depression.The profile of the wing (1) and (2) is followed at the said thin slice/edge of gable shape profile elements (3).
At this, the quantity of turbine flow passage (8) reaches four, perhaps increases to unlimited quantity but on principle, can be reduced to one.In each turbine flow passage (8), place the rotor that separates.Rotor (5) interconnects through the bearing in common shaft and the gable shape profile elements (3).Rotating energy transmits through the axle in the gear mechanism housing (6), in gear mechanism housing, changes into electric energy, mechanical energy or hydraulic pressure ability.Turbine flow passage (8) can be equipped with the turbine inlet thin slice (12) shown in Fig. 3 A and 3B.
Figure 15 A illustrates said embodiment with cross section.
Figure 15 B illustrates said embodiment with stereogram.
Figure 15 C illustrates the embodiment who is integrated in the building.
Figure 16 A and 16B illustrate and the similar embodiment of the invention of the principle of Figure 1B.
Figure 16 A illustrates the present invention with sectional view.
Figure 16 B illustrates the embodiment of the invention that is integrated in the building roof.
Figure 17 illustrates the embodiment of the invention of the cascade form that is similar to Fig. 8 C, at this, is installed on the towering building with Figure 1A-1F, 2A-2D, 3,4A-4B and all related the present invention of intermediate form.The present invention is suitable for being installed on all building bights.

Claims (15)

1. one kind is used for through using wind or fluid flow energy to generate the equipment of electric energy, mechanical energy or hydraulic pressure ability; Said equipment comprises at least one rotor (5), bottom profile part (4) and at least one wing at least; Said wind or fluid conductance cause the rotor axis rotation that rotates, and it is characterized in that:
Said rotor (5) axially is connected to generator, and
The said wing (1) is the wing of location, edge, and the string of the wing of location, wherein said edge is towards said rotor (5) orientation.
2. equipment as claimed in claim 1 is characterized in that, the wing of location, said edge has solid or hollow structure.
3. equipment as claimed in claim 1 is characterized in that, the perforation that the wing (1) of location, said edge has at least a portion that is positioned at the said wing.
4. equipment as claimed in claim 1 is characterized in that, the wing (1) of location, said edge has the edge notch.
5. equipment as claimed in claim 1 is characterized in that, the wing (1) of location, said edge has prismatic, smooth, protrusion, recessed perhaps different fluids dynamics Design.
6. like each described equipment among the claim 1-5, it is characterized in that the wing (1) of location, said edge is with an angular orientation, this angle is perpendicular to the angle of rotor (5) spin axis and be tangential between the angle of rotor (5) periphery.
7. equipment as claimed in claim 6; It is characterized in that; Said equipment further comprises at least one suspension arrangement, and the wing (1) of location, said edge is installed on the said suspension arrangement, and wherein said suspension arrangement comprises that the wing (1) of location, said edge can be around the spin axis of its rotation.
8. like each described equipment among the claim 1-6; It is characterized in that; Said equipment further comprises the wing (1) that is positioned at location, said edge and at least one the vertical wing (2) between the said rotor (5), and said vertical wing (2) is oriented its string and is substantially perpendicular to said rotor (5).
9. equipment as claimed in claim 8 is characterized in that, said vertical wing (2) is integrated in the wing (1) of location, said edge.
10. like claim 8 or 9 described equipment, it is characterized in that the wing cross section of said vertical wing (2) is a periphery that is prismatic, smooth, protrusion, recessed or that be adapted to said rotor (5).
11., it is characterized in that said rotor (5) is designed to vertical, level, propeller type or screw type turbo machine like each described equipment in the aforementioned claim.
12. as each described equipment in the aforementioned claim, it is characterized in that said equipment further comprises at least one thin slice (3) that is positioned at the turbine flow passage (8) that the wing (1) and said bottom profile part (4) by location, said edge define.
13., it is characterized in that the cross section of said bottom profile part (4) is a periphery that is smooth, crooked or that on aerodynamics, be adapted to said rotor (5) like each described equipment in the aforementioned claim.
14., it is characterized in that said equipment also comprises at least one the turbo machine thin slice (12) that is positioned at turbine flow passage (8) like each described equipment in the aforementioned claim.
15., it is characterized in that the wing (1) of location, two or more edges is oriented to their string facing to said rotor (5) like each described equipment in the aforementioned claim.
CN201080018693.7A 2009-04-28 2010-04-23 The combination wing utilized for the improvement of fluid flow energy and turbine equipment Expired - Fee Related CN102422014B (en)

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DKPA200900546A DK176999B1 (en) 2009-04-07 2009-04-28 Combined blade and turbine design for improved utilization of fluid flow energy
DKPA200900546 2009-04-28
PCT/DK2010/050092 WO2010124692A1 (en) 2009-04-28 2010-04-23 Combined wing and turbine device for improved utilization of fluid flow energy

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EP2425128B1 (en) 2018-12-19
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CN102422014B (en) 2015-11-25
EP2425128A1 (en) 2012-03-07

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